CN103754360A

CN103754360A - Similar flying saucer type rotaplane

Info

Publication number: CN103754360A
Application number: CN201410045540.1A
Authority: CN
Inventors: 鲍锋; 刘锦生; 傅向向
Original assignee: Xiamen University
Current assignee: Xiamen University
Priority date: 2014-02-08
Filing date: 2014-02-08
Publication date: 2014-04-30
Anticipated expiration: 2034-02-08
Also published as: CN103754360B

Abstract

The invention provides a similar flying saucer type rotaplane, and relates to an unmanned aerial vehicle. The invention provides a similar flying saucer type rotor unmanned aerial vehicle which fully utilizes the self-stabilization effect of a top. The rotaplane is provided with a plane body, plane wings, two motors, a variable pitch system and variable pitch propellers, wherein the plane body is connected with the roots of the plane wings, and the inside space of the plane body is used for loading airborne equipment; the plane wings which adopt small short-edge oval wing shapes are used for realizing conversion among the vertical take-off and landing state, hovering state and cruise of fixed wings; the two motors are mounted on the positions of the wing tips of the plane wings on two sides, and the rotating directions of the two motors are consistent; the variable pitch system is used for regulating the propeller pitch of the variable pitch propellers; the variable pitch system is used for regulating the propeller pitch of the propellers to change the thrust direction and the thrust of the propellers, and the switchover between a hovering mode and a cruise mode is realized. The structure is simple, the sensitivity to the center of the gravity of an airplane is weak, and the overall aerodynamic efficiency is high.

Description

One kind flying disc type cyclogyro

Technical field

The present invention relates to a kind of unmanned vehicle, particularly relate to a kind flying disc type cyclogyro that helicopter vertical takeoff and landing, hovering and the fixed wing aircraft mode of cruising can be combined.

Background technology

In order to design a kind of unmanned vehicle, make high-speed, the large voyage performance of its vertical takeoff and landing performance that has helicopter concurrently, unsettled delay and fixed wing aircraft, the mankind have proposed the various unmanned aerocrafts that possess vertical takeoff and landing ability, comprise compound un-manned aerial helicopter, the unmanned aerial vehicle of equipping thrust vectoring driving engine, rotor blade formula unmanned aerial vehicle, tilting duct screw propeller unmanned aerial vehicle, tilting rotor unmanned aerial vehicle etc.

In China, because the research to unmanned plane is started late, development high-speed, the unmanned vehicle of voyage performance greatly to the vertical takeoff and landing performance, hovering and the fixed wing aircraft that have helicopter concurrently also rests on theory and engineering research stage, does not still publish the pertinent data that any model is succeeded in developing.It is reported, domestic certain unit has developed the unmanned principle prototype of small-sized tilting rotor, the work of taking a flight test, and the tiltrotor of its overall plan and European and American countries is similar, is all to adopt to change rotor thrust direction, realizes the switching of landing and cruising condition.The maneuvering system more complicated of this scheme, cost are larger, very high to the requirement of material, and the rotor blade of this tiltrotor can only have the function of super-large diameter screw propeller concurrently when front flying, so propulsion coefficient is not high when front flying, has also limited aircraft and reached larger forward flight speed.In addition, when this class cyclogyro aloft hovers, the effective lift of the serious shielding when hovering impact main rotor of wing on main rotor slip-stream, and strict to the requirement of center of gravity front and back position during hovering.

Summary of the invention

The object of the invention is to, for existing the cruise defect of unmanned plane of vertical takeoff and landing, hovering and fixed-wing that has concurrently, provides and makes full use of the kind flying disc type rotor wing unmanned aerial vehicle of gyro from steady phenomenon.

The present invention is provided with fuselage, wing, two motors, displacement system and variable-distance screw propeller; Described fuselage is connected with wing root, and fuselage interior space is used for loading airborne equipment; Wing adopts the oval aerofoil profile of little minor face, for realizing the conversion between vertical takeoff and landing, hovering and fixed-wing cruising condition; Two motors are arranged on wing wing tip position, both sides, and two motor steerings are consistent, use displacement system to regulate the pitch of variable-distance screw propeller; Displacement system is for the pitch of propeller blades, and the thrust direction and the thrust size that to change screw propeller, produce, realize hovering and cruise mode and switch.

Described fuselage can adopt conical fuselage, and the certainly steady phenomenon while utilizing gyroscope High Rotation Speed, realizes its needed stability that takes off vertically.

The present invention uses the wing of low aspect ratio, and Airfoil uses the oval symmetrical airfoil of little minor face, but is not limited to ellipse, also can be the symmetrical airfoils such as rectangle.

Both sides wing can move entirely, and aspect control is by regulating the wing angle of attack or regulating nonuniform pitch propeller pitch to realize, but is not limited to this, also can use the control surface such as aileron, wing flap of conventional airplane to carry out attitude manipulation.

Two motors are arranged on wing tip position, but are not limited to use electric power, other energy such as also can use can fuel oil, combustible gas class.

Vertical takeoff and landing of the present invention, hovering and fixed-wing formula cruise between the switching of state be by change, to be positioned at the thrust direction that wing wing tip screw propeller produces to realize.When both sides screw propeller all produces pulling force, the present invention is in vertical takeoff and landing or hovering state, and when screw propeller one side produces thrust, a side generation pulling force, the present invention is in fixed-wing formula cruising condition.

Compare with existing vertical takeoff and landing, hovering and the fixed-wing unmanned plane technology of cruising that has concurrently, the present invention is simple in structure, and a little less than the sensivity of the center of gravity of airplane, overall pneumatic efficiency is higher.

Accompanying drawing explanation

Fig. 1 is the axle geodesic structure schematic diagram of the embodiment of the present invention.

Fig. 2 is the plan structure schematic diagram of the embodiment of the present invention.

Fig. 3 is vertical takeoff and landing and the hovering pattern of the embodiment of the present invention.

Fig. 4 is the flat pattern that flies of the vertical fixed-wing formula of the embodiment of the present invention.

Fig. 5 is the partial schematic diagram of the displacement system of the embodiment of the present invention.

The specific embodiment

Referring to Fig. 1～5, the embodiment of the present invention is provided with fuselage 1-1,1-2, wing 2-1,2-2, motor 3-1,3-2, and displacement system 4-1,4-2, variable-distance screw propeller 5-1,5-2.It is conical that fuselage 1-2 is, wing 2-1,2-2 section are little minor face ellipse, and be connected with fuselage 1-1 and can carry out certain angle of attack conversion, motor 3-1,3-2 are separately fixed at wing 2-1,2-2 wing tip position, two direction of motor rotation are consistent, are cw or rotate counterclockwise, mutually to overcome the present invention because motor rotates the moment of rotation producing, displacement system 4-1,4-2 are connected by pull bar 4-2-2 with screw propeller 5-1,5-2, can change the pitch of screw propeller 5-2-1.

The present invention can be according to mission requirements, realize vertical takeoff and landing, hovering and fixed-wing formula and cruise.As shown in Figure 3; for vertical takeoff and landing or hovering pattern; wing tip both sides screw propeller 5-1,5-2 all produce away from motor pulling force g1 and g2 respectively under the drive of motor 3-1,3-2; wing 2-1,2-2 both sides form the differential angle of attack as shown in Figure 3; class flying disc type cyclogyro produces rotational force R; and then form lift s1, s2, and then realize hovering of the present invention or vertical takeoff and landing.In Fig. 3, the hand of rotation that mark h1 and h2 are motor.

The present invention under cruise mode as Fig. 4, the screw propeller of one flank point produces away from motor pulling force g3, the screw propeller of opposite side wing tip produces the thrust g4 near motor, produce the B that makes a concerted effort that direction is consistent, wing 2-1,2-2 form the angle of attack of equidirectional as shown in Figure 4, the present invention and then generation lift s3, s4, the present invention can cruise as conventional fixed wing aircraft.In flight course, can be by changing that relative angle between wing 2-1,2-2 is adjusted aspect or by regulating the pitch of two variable screw propellers.In Fig. 4, the hand of rotation that mark h3 and h4 are motor.

Handoff procedure between vertical takeoff and landing, hovering pattern and cruise mode is:

1, from vertical takeoff and landing, hovering, switch and enter cruise mode, first need flight of the present invention to be increased to certain flying height, then moment disable motor 3-1,3-2, displacement system 4-2 changes the pitch of screw propeller 5-2 by pull bar 4-2-2 simultaneously, make it to form generation opposite force, wing 2-1,2-2 change over by the differential angle of attack positive incidence that direction is consistent, then restart motor 3-1,3-2, from hovering Mode-switch to cruising condition;

2, from cruise mode, switch vertical takeoff and landing, the hovering pattern of entering, first need the flying height that guarantees that the present invention is certain, then moment disable motor 3-1,3-2, displacement system 4-2 changes the pitch of screw propeller 5-2 by pull bar 4-2-2 simultaneously, make it to form generation opposite force, wing 2-1,2-2 change over the differential angle of attack by the differential angle of attack, then restart motor 3-1,3-2, enter hovering pattern.

Claims

1. a kind flying disc type cyclogyro, is characterized in that being provided with fuselage, wing, two motors, displacement system and variable-distance screw propeller; Described fuselage is connected with wing root, and fuselage interior space is used for loading airborne equipment; Wing adopts the oval aerofoil profile of little minor face, for realizing the conversion between vertical takeoff and landing, hovering and fixed-wing cruising condition; Two motors are arranged on wing wing tip position, both sides, and two motor steerings are consistent, use displacement system to regulate the pitch of variable-distance screw propeller; Displacement system is for the pitch of propeller blades, and the thrust direction and the thrust size that to change screw propeller, produce, realize hovering and cruise mode and switch.

2. a kind flying disc type cyclogyro as claimed in claim 1, is characterized in that described fuselage adopts conical fuselage.